EPPLER 397 AIRFOIL (e397-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 397 AIRFOIL (e397-il) Reynolds number: 100,000 Max Cl/Cd: 53.4 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e397-il-100000-n5.txt Download as CSV file: xf-e397-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 397 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3716 0.05654 0.05145 -0.1118 0.9396 0.0239
-9.750 -0.3824 0.04837 0.04298 -0.1230 0.9292 0.0238
-9.500 -0.3864 0.04245 0.03667 -0.1312 0.9163 0.0241
-9.250 -0.3767 0.03968 0.03373 -0.1338 0.9075 0.0248
-9.000 -0.3583 0.03696 0.03076 -0.1372 0.9016 0.0263
-8.750 -0.3432 0.03438 0.02777 -0.1391 0.8944 0.0287
-8.500 -0.3222 0.03247 0.02569 -0.1408 0.8884 0.0314
-8.250 -0.2943 0.03041 0.02328 -0.1433 0.8848 0.0353
-8.000 -0.2766 0.02917 0.02193 -0.1432 0.8774 0.0389
-7.750 -0.2498 0.02771 0.02013 -0.1446 0.8728 0.0448
-7.500 -0.2191 0.02649 0.01881 -0.1465 0.8697 0.0515
-7.250 -0.1986 0.02559 0.01778 -0.1463 0.8630 0.0577
-7.000 -0.1708 0.02461 0.01659 -0.1471 0.8584 0.0660
-6.750 -0.1393 0.02373 0.01556 -0.1487 0.8552 0.0759
-6.500 -0.1143 0.02307 0.01484 -0.1489 0.8502 0.0852
-6.250 -0.0888 0.02246 0.01413 -0.1491 0.8449 0.0957
-6.000 -0.0580 0.02180 0.01337 -0.1502 0.8413 0.1085
-5.750 -0.0249 0.02118 0.01263 -0.1517 0.8386 0.1230
-5.500 -0.0041 0.02093 0.01232 -0.1509 0.8322 0.1362
-5.250 0.0247 0.02054 0.01187 -0.1515 0.8281 0.1522
-5.000 0.0566 0.02013 0.01139 -0.1526 0.8250 0.1703
-4.750 0.0848 0.01987 0.01105 -0.1530 0.8210 0.1886
-4.500 0.1087 0.01974 0.01088 -0.1526 0.8156 0.2062
-4.250 0.1384 0.01952 0.01062 -0.1532 0.8120 0.2259
-4.000 0.1705 0.01927 0.01031 -0.1541 0.8091 0.2463
-3.750 0.1951 0.01923 0.01024 -0.1538 0.8043 0.2650
-3.500 0.2207 0.01920 0.01016 -0.1536 0.7995 0.2845
-3.250 0.2506 0.01906 0.00999 -0.1541 0.7962 0.3043
-3.000 0.2827 0.01890 0.00979 -0.1550 0.7935 0.3251
-2.750 0.3049 0.01900 0.00989 -0.1542 0.7882 0.3432
-2.500 0.3309 0.01902 0.00987 -0.1540 0.7837 0.3630
-2.250 0.3608 0.01893 0.00978 -0.1545 0.7805 0.3833
-2.000 0.3928 0.01880 0.00964 -0.1552 0.7780 0.4044
-1.750 0.4126 0.01902 0.00988 -0.1540 0.7723 0.4230
-1.500 0.4386 0.01907 0.00993 -0.1538 0.7680 0.4440
-1.250 0.4684 0.01901 0.00990 -0.1542 0.7649 0.4656
-1.000 0.5004 0.01892 0.00979 -0.1549 0.7625 0.4895
-0.750 0.5179 0.01924 0.01019 -0.1533 0.7563 0.5098
-0.500 0.5439 0.01930 0.01031 -0.1530 0.7523 0.5335
-0.250 0.5739 0.01926 0.01029 -0.1533 0.7493 0.5596
0.000 0.6048 0.01920 0.01026 -0.1538 0.7467 0.5874
0.250 0.6198 0.01961 0.01079 -0.1517 0.7401 0.6117
0.500 0.6462 0.01966 0.01090 -0.1514 0.7362 0.6408
0.750 0.6758 0.01960 0.01090 -0.1515 0.7334 0.6727
1.000 0.6967 0.01981 0.01120 -0.1502 0.7288 0.7044
1.250 0.7145 0.02005 0.01156 -0.1484 0.7232 0.7384
1.500 0.7391 0.02001 0.01162 -0.1474 0.7198 0.7783
1.750 0.7648 0.01984 0.01152 -0.1465 0.7172 0.8257
2.000 0.7702 0.02022 0.01207 -0.1423 0.7099 0.8935
2.250 0.8003 0.02024 0.01211 -0.1429 0.7057 1.0000
2.500 0.8352 0.02024 0.01204 -0.1443 0.7028 1.0000
2.750 0.8545 0.02076 0.01256 -0.1432 0.6967 1.0000
3.000 0.8797 0.02104 0.01283 -0.1431 0.6915 1.0000
3.250 0.9134 0.02104 0.01281 -0.1441 0.6882 1.0000
3.500 0.9343 0.02146 0.01325 -0.1432 0.6822 1.0000
3.750 0.9574 0.02177 0.01358 -0.1426 0.6763 1.0000
4.000 0.9918 0.02169 0.01351 -0.1437 0.6728 1.0000
4.250 1.0077 0.02224 0.01412 -0.1419 0.6654 1.0000
4.500 1.0351 0.02235 0.01426 -0.1419 0.6599 1.0000
4.750 1.0725 0.02211 0.01404 -0.1433 0.6563 1.0000
5.000 1.0810 0.02283 0.01486 -0.1403 0.6469 1.0000
5.250 1.1164 0.02259 0.01466 -0.1414 0.6422 1.0000
5.500 1.1280 0.02318 0.01535 -0.1389 0.6331 1.0000
5.750 1.1616 0.02295 0.01517 -0.1395 0.6274 1.0000
6.000 1.1734 0.02346 0.01578 -0.1370 0.6177 1.0000
6.250 1.2095 0.02308 0.01546 -0.1380 0.6113 1.0000
6.500 1.2161 0.02366 0.01615 -0.1346 0.6003 1.0000
6.750 1.2345 0.02384 0.01641 -0.1329 0.5907 1.0000
7.000 1.2629 0.02365 0.01628 -0.1326 0.5814 1.0000
7.250 1.2714 0.02412 0.01686 -0.1294 0.5684 1.0000
7.500 1.2847 0.02439 0.01720 -0.1269 0.5539 1.0000
7.750 1.3001 0.02460 0.01745 -0.1248 0.5378 1.0000
8.000 1.3141 0.02491 0.01779 -0.1225 0.5199 1.0000
8.250 1.3223 0.02557 0.01851 -0.1197 0.5005 1.0000
8.500 1.3350 0.02610 0.01907 -0.1174 0.4802 1.0000
8.750 1.3480 0.02669 0.01965 -0.1153 0.4588 1.0000
9.000 1.3578 0.02751 0.02046 -0.1130 0.4351 1.0000
9.250 1.3668 0.02845 0.02135 -0.1106 0.4097 1.0000
9.500 1.3741 0.02956 0.02237 -0.1082 0.3837 1.0000
9.750 1.3786 0.03093 0.02367 -0.1056 0.3571 1.0000
10.000 1.3819 0.03247 0.02514 -0.1032 0.3313 1.0000
10.250 1.3840 0.03420 0.02679 -0.1008 0.3064 1.0000
10.500 1.3851 0.03607 0.02859 -0.0985 0.2824 1.0000
10.750 1.3855 0.03811 0.03056 -0.0964 0.2582 1.0000
11.000 1.3857 0.04026 0.03264 -0.0944 0.2367 1.0000
11.250 1.3869 0.04242 0.03479 -0.0926 0.2158 1.0000
11.500 1.3871 0.04475 0.03708 -0.0910 0.1959 1.0000
11.750 1.3862 0.04728 0.03958 -0.0894 0.1760 1.0000
12.000 1.3850 0.04994 0.04219 -0.0880 0.1548 1.0000
12.250 1.3823 0.05286 0.04503 -0.0868 0.1353 1.0000
12.500 1.3812 0.05574 0.04787 -0.0857 0.1164 1.0000
12.750 1.3795 0.05877 0.05087 -0.0848 0.1009 1.0000
13.000 1.3785 0.06184 0.05393 -0.0840 0.0884 1.0000
13.250 1.3780 0.06494 0.05705 -0.0834 0.0782 1.0000
13.500 1.3768 0.06819 0.06032 -0.0829 0.0700 1.0000
13.750 1.3770 0.07137 0.06357 -0.0825 0.0629 1.0000
14.000 1.3753 0.07486 0.06712 -0.0823 0.0575 1.0000
14.250 1.3732 0.07849 0.07083 -0.0822 0.0528 1.0000
14.500 1.3687 0.08251 0.07487 -0.0823 0.0491 1.0000
14.750 1.3677 0.08613 0.07866 -0.0825 0.0449 1.0000
15.000 1.3635 0.09027 0.08287 -0.0828 0.0418 1.0000
15.250 1.3611 0.09420 0.08691 -0.0832 0.0386 1.0000
15.500 1.3603 0.09800 0.09088 -0.0838 0.0353 1.0000
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Polar data table (+)
Polar graphs
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